Aeroelastic Analysis and Optimization of High-aspect-ratio Composite Forward-swept Wings

In order to analyze the effects of forward-swept angle and skin ply-orientation on the static and dynamic aeroelastic characteristics, the aeroelastic modeling and calculation for high-aspect-ratio composite wings with different forward-swept angles and skin ply-orientation are performed. This paper presents the results of a design study aiming to optimize wings with typical forward-swept angles and skin ply-orientation in an aeroelastic way by using the genetic/sensitivity-based hybrid algorithm. Under the conditions of satiated multiple constraints including strength, displacements, divergence speeds and flutter speeds, the studies are carried out in a bid to minimize the structural weight of a wing with the lay-up thicknesses of wing components as design variabies. In addition, the effects of the power of spanwise variation function of lay-up thicknesses of skins and iugs on the optimized weights are also analyzed.

Structural Modeling and Aeroelastic Analysis of High-Aspect-Ratio Composite Wings

A unified structural model for high-aspect-ratio composite wing with arbitrary cross-section is developed. Two types of lay-ups of the composite wing, namely, circumferentially uniform stiffness （CUS） configuration and circumferentially asymmetric stiffness （CAS） configuration, are investigated. The present structural modeling method is validated through ANSYS FEM software for the case of a composite box beam. Then, the case of a single-cell composite wing with NACA0012 airfoil shape is considered. To investigate the aeroelastic problem of high-aspect-ratio composite wings, the linear ONERA aerodynamic model is used to model the unsteady aerodynamic loads under the case of small angle of attack. Finally, flutter speeds of the high-aspect-ratio wing with various composite ply angles are determined by using U-g method.

Stall Flutter Analysis of High-Aspect-Ratio Composite Wing

The stall flutter characters of high-aspect-ratio composite wing are investigated, and the effects of structure geometric nonlinearity and stiffness couple created by composite anisotropy on them also are discussed. Firstly, the high-aspect-ratio wing is modeled as a composite thin-walled closed section Euler beam whose displacement and rotation both could be of finite value, and the nonlinear dynamic equations is build up on it with all the effects of geometric nonlinearity, aerodynamic nonlinearity and anisotropy of material being considered. Then vibration equations are deduced through perturbing the dynamic equations at wing＇s equilibrium position, and coupled with unsteady stall aerodynamic model and ONERA model, to obtain the nonlinear stall flutter analysis equations of wing. Finally, the flutter stabilities with various wind speeds are determined by the harmonic balance method. With several exampies, the validity of the stall flutter model is proved, and the significant effects of geometric nonlinearity on the stall flutter various characters as wall as the effects of ply angle on the stall flutter speed and frequency also are discussed.

Optimization of Lower Hybrid Current Drive Efficiency for EAST Plasma with Non-Circular Cross Section and Finite Aspect-Ratio

The two-dimensional equilibrium with flexible boundaries is solved via using a MAT- LAB Equilibrium Code （MEC）, which has applied the finite element method to handle the change- able plasma shape and employed the trust-region dogleg method to solve the nonlinear partial dif- ferential equation. The corresponding driven current profile is also calculated by coupling with the lower-hybrid simulation code （LSC）. The results are applied to optimize the lower hybrid current drive （LHCD） efficiency for the Experimental Advanced Superconductor Tokamak （EAST） and suggested that both elongation and triangularity have a notable effect on the efficiency because of the competition between the increase in the resonant area and in the Shafranov shift. Moreover, large aspect-ratio has a negative effect on the efficiency. These effects are studied numerically, which might be considered carefully for both good plasma confinement and high LHCD efficiency.

Development of high-aspect-ratio microchannel heat exchanger based on multi-tool milling process

A high-aspect-ratio microchannel heat exchanger based on multi-tool milling process was developed. Several slotting cutters were stacked together for simultaneously machining several high-aspect-ratio microchannels with manifold structures. On the basis of multi-tool milling process, the structural design of the manifold side height, microchannel length, width, number, and interval were analyzed. The heat transfer performances of high-aspect-ratio microchannel heat exchangers with two different manifolds were investigated by experiments, and the influencing factors were analyzed. The results indicate that the magnitude of heat transfer area per unit volume dominates the heat transfer performances of plate-type micro heat exchanger, while the velocity distribution between microchannels has little effects on the heat transfer performances.

Stiffness Distribution and Aeroelastic Performance Optimization of High-Aspect-Ratio Wings

The relationship between stiffness distribution and aeroelastic performance for a beam-frame model and a3-D model is investigated based on aeroelastic optimization of global stiffness design for high-aspect-ratio wings.The sensitivity information of wing spanwise stiffness distribution with respect to the twist angle at wing tip,the vertical displacement at wing tip,and the flutter speed are obtained using a sensitivity method for both models.Then the relationship between stiffness distribution and aeroelastic performance is summarized to guide the design procedure.By using the genetic/sensitivity-based hybrid algorithm,an optimal solution satisfying the strength,aeroelastic and manufacturing constraints is obtained.It is found that the summarized guidance is well consistent with the optimal solution,thus providing a valuable design advice with efficiency.The study also shows that the aeroelastic-optimization-based global stiffness design procedure can obtain the optimal solution under multiple constraints with high efficiency and precision,thereby having a strong application value in engineering.

Design and Simulation of BTT Missile with High-Aspect-Ratio Wing Robust H_∞ Autopilot

For the strong coupling among the channels of bank-to-turn （BTT） missile with high-aspect-ratio wing, an autopilot is designed with a two loop control structure robust autopilot design methods. By the inner loop design, the question of pole-zero cancellation is solved, and the stabilization of structured uncertainty is achieved. Through the outer loop of H∞ controller design, the flying performance and robustness can be guaranteed. The nonlinear simulation results show that the autopilot designed has perfect time domain response, and can suppress bad influence of the inertial and kinematics couplings. It can make the missile fly stably in the large flying areas. The control is very effective.

Selective Area Growth of GaAs in V-Grooved Trenches on Si(001) Substrates by Aspect-Ratio Trapping

A high quality of GaAs crystal growth in nanoscale V-shape trenches on Si（O01） substrates is achieved by using the aspect-ratio trapping method. GaAs thin films are deposited via metal-organic chemical vapor deposition by using a two-step growth process. Threading disJocations arising from lattice mismatch are trapped by laterally confining sidewalls, and antiphase domains boundaries are completely restricted by V-groove trenches with Si { 111} facets. Material quality is confirmed by scanning electron microscopy （SEM）, transmission electron microscopy （TEM） and high resolution X-ray diffraction. Low temperature photoluminescence （PL） measurement is used to analyze the thermal strain relaxation in GaAs layers. This approach shows great promise for the realization of high mobility devices or optoelectronie integrated circuits on Si substrates.

Electrodeposition of Gold to Conformally Fill High-Aspect-Ratio Nanometric Silicon Grating Trenches: A Comparison of Pulsed and Direct Current Protocols

Filling high-aspect-ratio trenches with gold is a frequent requirement in the fabrication of X-ray optics as well as micro-electronic components and other fabrication processes. Conformal electrodeposition of gold in sub-micron-width silicon trenches with an aspect ratio greater than 35 over a grating area of several square centimeters is challenging and has not been described in the literature previously. A comparison of pulsed plating and constant current plating led to a gold electroplating protocol that reliably filled trenches for such structures.

高深宽比梳齿结构刻蚀工艺

梳齿结构刻蚀是制备电容加速度计芯片的重要工序步骤。在梳齿结构刻蚀过程中,采用快速切换阀代替质量流量控制器(MFC)开关气体解决了梳齿侧壁弯曲问题;将Bosch工艺中物理轰击步骤和化学刻蚀步骤移到沉积步骤之前解决了梳齿顶部损伤问题;研究了沉积时间、物理轰击偏置电极功率、化学刻蚀压力与刻蚀选择比的关系。实验结果表明:增加化学刻蚀压力能够显著提升刻蚀选择比,但齿间隙也会随着化学刻蚀压力的增加而展宽,优化后的Bosch工艺配方为沉积时间1.3 s,物理轰击偏置电极功率70 W,化学刻蚀压力60 mTorr(1 mTorr≈0.133 Pa)。制备的梳齿结构齿间隙宽度3.19μm,深度86.3μm,侧壁倾角89.9°,侧壁粗糙度79 nm,深宽比达到27∶1,刻蚀选择比达到32∶1,并成功应用于电容加速度计芯片生产。

基于原位微观图像的含蜡原油析蜡胶凝过程

原油的流变性是石油开采、输运过程关注的基础物性,含蜡原油具有复杂的低温流变特性,而蜡的析出是决定原油低温胶凝和复杂流变性的内因。采用可以记录蜡晶微观结构实时演变过程的原位显微观测技术,以大庆原油为考察对象研究了含蜡原油降温析蜡胶凝过程蜡晶微观形貌变化。结果表明:大庆原油在实验温度34~60℃范围内降温过程中,蜡晶数量和面积先缓慢增加后以近似指数形式增加,平均长径比由波动逐渐趋于稳定,分形维数由降温初始阶段波动式增加过渡到后续的线性增加。在降温的开始阶段,降温速率(0.25、0.50、1.00、1.50、2.00℃/min)和加热温度(50、55、57、60、65℃)对蜡晶析出生长过程影响不明显;随着降温的持续,降温速率的减小或加热温度的升高,蜡晶数量和蜡晶面积均大幅增大。蜡晶微观参数在65℃发生突变,这与宏观流变实验的改性加热温度相吻合。含蜡原油降温析蜡胶凝过程的蜡晶生长规律为含蜡原油复杂宏观流变性深入研究及改性输送技术提供理论基础。

一种用于MCP的新型防离子反馈膜

传统技术制备的MCP防离子反馈膜在一定程度上会影响像管的信噪比,长时间的工作条件下也会降低像管的可靠性,基于传统防离子反馈膜缺陷导致的像管信噪比和可靠性性能亟需改善和提高的迫切需求,开展一种用于MCP的新型防离子反馈膜研究。采用原子层沉积技术(Atomic Layer Deposition,ALD)在有较高长径比的MCP通道内壁及输入端的通道孔处制备一层连续的高质量U型结构的防离子反馈膜,经MCP综合检测装置测试,与传统技术制备的MCP部件性能相比,新型防离子反馈膜致密,增益值较高,部件含碳量低,新型防离子反馈膜的MCP部件经制管后像管信噪比高,寿命可靠性高,此技术制备的新型防离子反馈MCP部件对与像增强器信噪比和可靠性性能的提升具有重要意义。

长高比对隔离段激波串特性的影响研究

隔离段是双模态超燃冲压发动机能够在不同飞行马赫数下以超燃和亚燃模态工作的核心部件。为了研究双模态超燃冲压发动机隔离段设计中长高比对隔离段激波串特性和超音速流动的影响,对以长280 mm、高30 mm的矩形隔离段为基准的一系列隔离段进行数值模拟研究。首先将计算得到的基准隔离段中心壁面压力和第一道激波位置与实验数据进行比较,验证数值模拟的准确性与合理性;进而分析在相同来流条件下,不同长高比对隔离段内激波串的形成位置、压力分布、速度分布等流动特性的影响。研究发现:随着隔离段长高比的增大,隔离段抗反压能力相应增强,激波串位置随之后移,激波强度减弱,激波串结构更加紧密,发生附面层分离及转捩的位置更靠近隔离段的出口位置,隔离段内的空气堵塞程度减小。

基于PSO-CNN-XGBoost水下柱形装药峰值超压预测

为探索水下柱形装药结构、爆距等参数与水下柱形装药峰值超压的关系,将装药样本数据视为二维数据,建立粒子群优化(Particle Swarm Optimization,PSO)算法、一维卷积神经网络(1D Convolutional Neural Network,1DCNN)和极端梯度提升(Extreme Gradient Boosting,XGBoost)的水下柱形装药峰值超压融合预测算法。采用相关性分析与数据可视化方法,分析装药结构参数、爆距与峰值超压之间的关联关系。设计1DCNN深度网络挖掘不同长径比、爆距等参数与峰值超压之间的纵向时序关系。运用XGBoost算法寻找装药结构参数、爆距与峰值超压之间的横向非线性关系,提升小样本数据的预测精度。使用PSO算法优化1DCNN和XGBoost的超参数,获得最优算法结构。研究结果表明,在包含10种智能算法的对比实验中,PSO-CNN-XGBoost水下柱形装药峰值超压预测算法在精度、稳定性、拟合程度上均高于其他模型。

气体流量和喷嘴直径对鼓泡塔内气泡大小和形状分布的影响

通过高速摄影结合图像处理算法,研究气体流量和喷嘴直径对气泡尺寸和纵横比分布的影响。结果表明,在所有喷嘴直径下,气泡当量直径的概率密度呈现双峰分布,其中第一个峰值接近直径为1.5~2 mm的小气泡区域,另一个峰值位于较大的气泡区域。将气体流量从0.1 L/min增加到0.2 L/min会导致大气泡的概率密度更高,表明气泡聚并现象普遍存在。当气体流量增加至1.2L/min时,峰值对应的气泡直径变小,并且气泡破裂占主导地位。对于直径为1~2 mm的气泡,形状受气体流量的影响较小,而3~9 mm的气泡在所有气体流量下气泡纵横比概率密度分布的峰值均位于纵横比E=0.5处。Iguchi和Chihara提出的模型能更好地预测气泡脱离直径随气体流量的增大的变化。

大跨度铁路桥附属构件对不同宽高比矩形断面涡振性能的影响

在已建成的大跨度鳊鱼洲长江大桥原设计宽高比为6.7∶1的四线铁路桥矩形箱型主梁断面的基础上,通过调整断面宽高比,设计宽高比为4∶1的二线铁路和宽高比为9∶1的六线铁路桥矩形箱梁断面。通过节段模型风洞试验,在0°,±3°和±5°风攻角的均匀来流下,对以上3种常用二线、四线和六线铁路桥矩形箱梁断面与对应相同宽高比纯矩形断面之间的涡振特性关系,以及铁路桥附属构件对不同宽高比矩形断面涡振性能的影响进行研究。结果表明:在宽高比分别为4∶1和6.7∶1的矩形断面上布置铁路桥附属构件能增大断面在负风攻角下的涡振振幅,在-5°风攻角下竖向涡振振幅增大率高达277.5%,但对正风攻角下的涡振响应起到一定的抑制作用,而在宽高比为9∶1的矩形断面布置六线铁路桥附属构件则能明显增大该断面在各风攻角下的涡振振幅,其扭转涡振振幅增大率均在48.3%以上;铁路桥附属构件对矩形断面涡振性能的降低作用随着断面宽高比的增大而提升,针对气动外形较钝的二线和四线铁路桥箱梁,可参考相似宽高比矩形断面涡振特性,并重点考察箱梁在负风攻角下的涡振响应,而针对宽高比较大的六线铁路桥箱梁,由于附属构件影响较大,参考相似宽高比矩形断面涡振特性的意义较小,均应详细研究其在各风攻角下的涡振性能。

顺序凝固工艺对大长径比装药缩松的影响研究

针对顺序凝固工艺对大长径比装药易形成缩松的问题,分别以受控生长期、自由凝固期的相界面形貌特征参数为中间量,建立了工艺参数到缩松体积的4层关联路径,选择TNT/RDX(33.8/65)炸药、长径比5∶1的装药模具,进行了正交仿真、极差分析以及Spearman相关系数计算,结果表明,降低水温、入水速度以及提高环境换热系数可提高受控生长期的相界面高度、开口角,从而降低自由凝固期的凝固区间最大厚度,最终减少缩松体积;工艺参数影响强弱为:水温、入水速度、环境换热系数;降低入水速度、提高环境换热系数可减少对低水温的依赖。本研究探明了顺序凝固工艺参数对大长径比装药相界面演化及缩松的影响机理,可为相关工艺设计提供理论支撑。

融合多源数据挖掘信息的非轴对称端壁/叶身联合成型设计空间知识挖掘

为厘清联合成型设计空间各造型方法对涡轮叶栅性能提升的贡献,将基于总变差分析的全局敏感性分析方法与平行坐标系及直方图、散点图等可视化技术相结合,提出了将多源数据挖掘信息进行融合的设计空间知识挖掘框架,并利用该框架对某小展弦比叶栅端壁/叶身联合成型设计空间进行知识挖掘。结果表明:叶栅气动损失增减对基元型线微调十分敏感;非轴对称端壁所带来的损失减少量与型线微调接近,但设计空间内不同非轴对称端壁样本性能波动较小,导致其重要性被全局敏感性分析方法低估;虽然单独采用弯叶片难以整体降低小展弦比叶栅损失,但将弯、型线微调和非轴对称端壁造型相结合可获得“1+1+1>3”的性能增益;在端壁/叶身联合成型设计空间内,将基元型线朝着后加载方向微调,并采用喉部附近下凹较深的非轴对称端壁造型及反弯叶片设计,可获得气动损失较小的叶栅设计。研究结果明晰了端壁/叶身联合成型设计空间优化解特征,可为类似小展弦比叶栅设计优化提供借鉴。

不同浓度离子溶液中气泡运动特性的实验研究

气泡运动特性可以分析流型形成和演化,是探究两相流模型构建的基础。为了进一步研究气泡在多种溶液内的运动特性,搭建了气泡运动特性实验平台。在3种浓度的FeCl_(3)、CaCl_(2)、NH_(4)Cl离子溶液及去离子水内,对单个气泡运动特性进行了实验研究,利用高速相机拍摄图片并导入MATLAB软件进行了计算。据此,分析了离子溶液内单个气泡的上升时间,脱离时间,初始当量直径,以及纵横比。结果表明:离子溶液,尤其是CaCl_(2)溶液在一定程度上可以促进气泡在喷嘴处的脱离,使得脱离时间减少,当喷嘴为1.5 mm时,促进作用最为明显;三种离子溶液和去离子水比较,气泡上升时间都有所缩短,但是相差不大;三种离子溶液中,FeCl_(3)溶液中气泡纵横比变化最大;NH_(4)Cl溶液对气泡的当量直径促进作用最强,CaCl_(2)溶液会抑制气泡当量直径的发展,因此在特殊流体机械内部,应适当增加钙离子以降低冲击带来的腐蚀与振动;在去离子水和三种离子溶液中气泡的纵横比δ都会有一个“L”型分布,且最大值均出现在气泡脱离喷嘴的瞬间。

基于距离感知的金属缺陷样本标签分配算法

针对金属表面缺陷检测模型在训练过程中正负样本分配时不考虑金属表面缺陷的宽高比、对目标分布的定位能力差等问题,提出了距离感知的动态标签分配(DDA)算法。DDA不改变原有检测模型的结构也不增加计算开支,根据真实框的几何特性提出新的距离损失计算范式,以优化宽高比悬殊的回归问题,将迭代过程中的回归偏移量解码为预测框坐标,最后计算预测框、锚框和真实框三者之间综合交并比信息,动态地选择正负样本以提高训练精度。在武汉某钢厂冷轧带钢表面缺陷检测中进行了验证,并引入公开的热轧带钢表面缺陷数据集进行了泛化试验,检测效果均有显著改善,对金属表面质量规范有实际应用价值。